Multi-Objective, Multi-Disciplinary Design Optimization and Multi-Attribute Evaluation of Hybrid Rocket Motors Used for Manned Lunar Lander

This paper proposed a multi-objective, multi-disciplinary design optimization and multi-attribute evaluation method for the manned lunar lander descent stage. A system model is established considering multiple disciplines such as propulsion, structure, trajectory cost. With goal of minimizing mass, cost maximizing velocity increment, overall scheme hybrid rocket motors was optimized by altering various grain shapes feed systems, acting an alternative propulsion lander. Under same conditions, optimal continuous discrete attributes studied compared with that liquid engines to elucidate characteristics deep space exploration. The results showed obtained only were different from those both attributes. oxygen/kerosene superior schemes due its excellent specific impulse performance when are considered. However, have shown good in terms operability, manufacturability, safety environmental protection. So, after introducing attributes, show greater potential. In brief, based on comprehensive motor provided tube gas pressure considered Furthermore, parametric analysis fuel outside diameter, initial thrust oxygen-to-fuel ratio had significant influence lander, particular, effect diameter more than 50%.